AMS 5596 - Inconel 718 Sheet, Strip, Foil & Plate (Solution Annealed)
AMS 5596 is the SAE International aerospace material specification for Inconel 718 (UNS N07718), a precipitation-hardenable nickel-chromium-iron superalloy with niobium, molybdenum, aluminum, and titanium, supplied in the form of sheet, strip, foil, and plate in the solution annealed condition.
Inconel 718 is the most widely used nickel-base superalloy in aerospace, accounting for approximately one-third of all nickel superalloy production by weight.
In the solution annealed condition per AMS 5596, Inconel 718 achieves a minimum tensile strength of 150 ksi (1034 MPa) and a minimum yield strength of 75 ksi (517 MPa) with a minimum elongation of 30%. The alloy maintains useful strength and oxidation resistance at temperatures up to 1300°F (704°C) under mechanical load, and oxidation resistance extends to 1800°F (982°C). AMS 5596 is the standard procurement specification for Inconel 718 flat-rolled products used in jet engine components, gas turbine hot-section hardware, aerospace structural sheet metal, and high-temperature fastener blanks.
AMS 5596 Available Forms and Stocked Sizes
AMS 5596 covers Inconel 718 in flat-rolled forms. The SAE/AMS definitions for thickness ranges are:
Thickness: below 0.006 inches (0.15 mm)
Thickness: 0.1875 inches (4.76 mm) and above
Thickness: 0.006–0.1874 inches; width ≤ 9.250 inches
Thickness: 0.006–0.1874 inches; width > 9.250 inches
Fighter Jet Metals stocks and supplies AMS 5596 Inconel 718 sheet and plate in standard and custom-cut sizes with same-day quote response. Plate saw cutting, shearing, and laser cutting services are available in-house.
Applications of AMS 5596
Aerospace & Gas Turbine Applications
- Jet engine combustion casing and intermediate case structures
- Compressor discs, vanes, and blades (mid-stage compressor where temps are below 1300°F)
- Engine nacelle and thrust reverser sheet metal components
- Afterburner liner and hot-gas-path sheet metal fabrications
- High-temperature bolts, studs, and fasteners for engine and airframe
- Turbine rear frame and exhaust nozzle structures
- Spacecraft and launch vehicle components requiring high strength-to-weight ratio
Defense & Industrial Applications
- Rocket motor cases and pressure vessel forgings (in bar form, AMS 5662/5663/5664)
- Nuclear reactor component structures and shielding
- Downhole oil and gas completion tools and wellhead equipment
- High-temperature tooling, fixtures, and dies for metalforming
- Heat exchanger tubing and baffles for corrosive high-temperature service
- Cryogenic applications – excellent toughness retained at liquid nitrogen temperatures (−320°F / −196°C)
Precision Sheet Metal & Fabrication
- Formed sheet metal shells, brackets, and clips in aircraft engine bays
- Laser-cut and waterjet-cut blanks for machined turbine components
- Spot-welded and seam-welded assemblies for engine sheet metal fabrications
- Near-net-shape blanks for die forming complex curvature components
- Honeycomb panel face skins for thermal insulation structures
Chemical Composition - AMS 5596
The following chemical composition limits apply to Inconel 718 (UNS N07718) per AMS 5596
| Element | Symbol | Minimum % | Maximum % |
|---|---|---|---|
| Nickel + Cobalt | Ni+Co | 50.0 | 55.0 |
| Chromium | Cr | 17.0 | 21.0 |
| Iron | Fe | Balance | - |
| Niobium + Tantalum | Nb+Ta | 4.75 | 5.50 |
| Molybdenum | Mo | 2.80 | 3.30 |
| Boron | B | - | 0.006 |
| Cobalt | Co | - | 1.00 |
| Titanium | Ti | 0.65 | 1.15 |
| Aluminum | Al | 0.20 | 0.80 |
| Carbon | C | - | 0.08 |
| Manganese | Mn | - | 0.35 |
| Silicon | Si | - | 0.35 |
| Phosphorus | P | - | 0.015 |
| Sulfur | S | - | 0.015 |
| Copper | Cu | - | 0.30 |
Nickel and chromium form the base matrix, providing oxidation and corrosion resistance.
Niobium (4.75–5.50%) is the most critical alloying element in Inconel 718 – it forms the Ni₃Nb gamma-double-prime (γ”) phase, which is the primary hardening precipitate responsible for the alloy’s exceptional age-hardening response.
This is distinct from most other nickel superalloys, which harden via gamma-prime (γ’) phases based on aluminum and titanium.
The γ” phase in Inconel 718 has a relatively slow precipitation kinetics – this is why the alloy has outstanding weldability and resistance to strain-age cracking, compared to alloys like A286 or Waspaloy. Molybdenum provides solid-solution strengthening.
Aluminum and titanium contribute to gamma-prime (γ’) precipitation as a secondary hardening phase.
Iron content (balance, approximately 18–19%) makes Inconel 718 one of the most cost-effective nickel superalloys.
Mechanical Properties - AMS 5596
Minimum mechanical properties required by AMS 5596 for Inconel 718 sheet, strip, foil, and plate in the solution annealed condition:
| Property | Imperial | Metric |
|---|---|---|
| Tensile Strength (min) | 150,000 psi (150 ksi) | 1034 MPa |
| Yield Strength, 0.2% offset (min) | 75,000 psi (75 ksi) | 517 MPa |
| Elongation in 2 in. (min) | 30% | 30% |
Elevated Temperature Properties - AMS 5596
Inconel 718 per AMS 5596 retains useful strength at temperatures well above conventional stainless steels and most other structural alloys. Typical tensile properties at elevated temperature (solution annealed + aged condition – representative values from published literature):
| Temperature | Tensile Strength (typical) | Yield Strength (typical) | Elongation (typical) |
|---|---|---|---|
| Room Temp (70°F / 21°C) | 200 ksi (1379 MPa) | 170 ksi (1172 MPa) | 20% |
| 400°F (204°C) | 190 ksi (1310 MPa) | 162 ksi (1117 MPa) | 19% |
| 800°F (427°C) | 183 ksi (1262 MPa) | 158 ksi (1089 MPa) | 18% |
| 1000°F (538°C) | 181 ksi (1248 MPa) | 156 ksi (1075 MPa) | 17% |
| 1200°F (649°C) | 170 ksi (1172 MPa) | 148 ksi (1020 MPa) | 15% |
| 1300°F (704°C) | 155 ksi (1069 MPa) | 135 ksi (931 MPa) | 14% |
Physical Properties - AMS 5596
| Property | Value (Imperial) | Value (Metric) |
|---|---|---|
| Density | 0.296 lb/in³ | 8.19 g/cm³ |
| Melting Range | 2300°F–2437°F | 1260°C–1336°C |
| Modulus of Elasticity | 29.0 × 10⁶ psi | 200 GPa |
| Thermal Conductivity | 6.5 BTU/(hr·ft·°F) | 11.2 W/(m·K) |
| Thermal Conductivity (1800°F) | 9.8 BTU/(hr·ft·°F) | 17.0 W/(m·K) |
| Coefficient of Thermal Expansion | 7.2 × 10⁻⁶ /°F | 13.0 × 10⁻⁶ /°C |
| Specific Heat | 0.104 BTU/(lb·°F) | 435 J/(kg·K) |
| Max Service Temperature (Mechanical Load) | 1300°F | 704°C |
| Max Service Temperature (Oxidation Resistance) | 1800°F | 982°C |
| Melt Practice | VIM + VAR (double melt) | VIM + VAR |
AMS 5596 vs AMS 5597 - Key Differences
AMS 5596 and AMS 5597 both cover Inconel 718 in the same flat product forms (sheet, strip, foil, plate) but in fundamentally different heat treatment conditions.
| Feature | AMS 5536 | AMS 5754 |
|---|---|---|
| Alloy | Inconel 718 (UNS N07718) | Inconel 718 (UNS N07718) |
| Product Forms | Sheet, Strip, Foil, Plate | Sheet, Strip, Foil, Plate |
| Condition | Solution Annealed | Solution Annealed + Precipitation Hardened |
| Tensile Strength Min | 150 ksi (1034 MPa) | 185 ksi (1276 MPa) |
| Yield Strength Min | 75 ksi (517 MPa) | 150 ksi (1034 MPa) |
| Elongation Min | 30% | 12% |
| Hardness (typical) | ~Rc 28 | ~Rc 40 |
| Formability | Excellent - suitable for forming, stamping, bending | Limited - fully hardened; forming not practical |
| Weldability | Excellent | Reduced - risk of heat-affected zone cracking |
| When to Use | Raw material for forming, welding, and sheet metal fabrication | Final delivery condition for machined or flat-section components requiring full strength |
If you are forming, welding, or fabricating sheet metal – procure to AMS 5596 (solution annealed, ductile).
If the drawing specifies the final part must be in the fully aged condition – procure to AMS 5597.
Most sheet metal assemblies are procured to AMS 5596, fabricated, and then precipitation hardened as a completed assembly.
AMS 5596 Machining Guidelines
Inconel 718 in the solution annealed condition (AMS 5596) is significantly easier to machine than the precipitation-hardened condition.
However, it is still considerably harder to machine than stainless steel.
- Cutting speeds: Low (30–60 SFM for carbide tooling in solution annealed condition; lower still after aging)
- Feeds: Moderate chip loads; never rub – Inconel 718 work hardens rapidly and aggressively
- Tooling: Sharp, positive-rake carbide inserts; PVD-coated carbide (TiAlN or TiCN) for longer tool life; ceramic inserts for high-speed roughing
- Coolant: High-pressure, high-volume flood coolant required at all times – sulfo-chlorinated or water-soluble
- Work hardening: Inconel 718 work hardens more severely than most other nickel alloys – consistent feed, no dwell, no rub
- Sequence recommendation: Machine in the solution annealed condition where possible; precision machine after aging only for final dimensions
- Key difference from stainless: IN718 is 3–5× harder to machine than 304 SS; requires 50–60% lower cutting speeds
- Comparison: Harder to machine than Hastelloy X (AMS 5536) or A286 (AMS 5525); typical machining speed for IN718 bar is 40-50 SFM vs. 80+ SFM for those alloys
AMS 5596 Weldability
Inconel 718 per AMS 5596 has exceptional weldability for a high-strength nickel superalloy – this is one of its defining advantages over other precipitation-hardenable alloys such as Waspaloy, René 41, and Udimet 720.
- GTAW (TIG): Primary process for thin sheet; argon or argon-helium shielding
- GMAW (MIG): Suitable for thicker plate sections
- PAW (Plasma Arc): Used for precision aerospace sheet metal joints
- Electron Beam (EBW): High-precision vacuum welding for critical aerospace components
- Resistance welding: Spot and seam welding applicable for thin sheet assemblies
- Filler metal: ERNiCrMo-3 (Inconel 625 filler) is the most common choice for IN718 sheet welds; matching ERNiFeCr-2 (IN718 filler) is used when full age-hardened strength in the weld is required
- Pre-heat: Not required for IN718 in the solution annealed condition
- Interpass temperature: Keep below 300°F (149°C)
- Post-weld heat treatment: Full solution anneal + two-stage precipitation hardening cycle is required for maximum weld strength. If only partial aging is performed, weld zone strength will be below base metal
- Key weldability advantage: Inconel 718 is NOT susceptible to strain-age cracking – unlike Waspaloy, René 41, and other γ’-hardened alloys. This is because γ” precipitation kinetics in IN718 are slow, allowing stress relaxation before hardening occurs during post-weld heat treatment.
- AMS 5596 vs AMS 5597 for welding: Always weld in the solution annealed condition (AMS 5596). Never attempt to weld IN718 that has already been precipitation hardened (AMS 5597) – the result is unacceptable HAZ cracking.
Why AMS 5596 Inconel 718 - The High-Strength Aerospace Sheet Standard
Inconel 718 occupies a unique position in the aerospace materials universe as the highest-strength nickel alloy that is readily weldable and formable. When a design requires:
Inconel 718 provides 2–3× the strength at elevated temperature; required when service temperature exceeds 1000°F (538°C) or when cryogenic toughness is critical
Inconel 718 provides approximately 40–50% higher strength in the hardened condition (185+ ksi vs. 130 ksi); IN718 is preferred for the most highly stressed structural components
IN718 is easier to form, weld, and fabricate; Waspaloy has marginally higher strength above 1300°F (704°C) and is used for the hottest disk applications where IN718 overages
IN718 provides much higher strength in the hardened condition; Inconel 625 has better aqueous corrosion resistance and is preferred for cladding and corrosion-barrier applications
Inconel 718 has ~2× the strength at temperatures up to 1300°F (704°C); Hastelloy X is preferred above 1400°F (760°C) where IN718 overages and loses strength
AMS 5596 Cross-Reference Specifications
SHEET & PLATE
Sheets and plates for high-temperature aerospace and industrial applications.
BARS & FORGINGS
Bars and forgings designed for high-strength, creep, and fatigue-resistant components.
BOEING SPECIFICATIONS
Boeing-approved Nickel 718 for airframe and engine parts.
GE Aviation
Engine components requiring high-temperature strength and durability.
MTU AERO ENGINES
Gas turbine bars and forgings with precise heat treatment and mechanical properties.
PRATT & WHITNEY PWA
Engine shafts, discs, and high-stress components with strong fatigue and creep resistance.
SNECMA / SAFRAN
High-performance turbine parts and engine components for French aircraft engines.
ISRAEL AEROSPACE INDUSTRIES
Nickel 718 for defense and aerospace applications with strict mechanical and chemical standards.
Trade Names and Equivalent Designations
Inconel 718 per AMS 5596 is known by several designations across different standards systems:
| Designation | System | Notes |
|---|---|---|
| Inconel 718 | Trade name | Original designation by Special Metals (now Precision Castparts) |
| IN-718 / IN718 | Common abbreviation | Widely used in design documents and procurement |
| UNS N07718 | UNS (Unified Numbering System) | Standard material identifier in North America |
| W.Nr. 2.4668 | Werkstoffnummer (DIN/EN) | European material number |
| NiCr19Fe19Nb5Mo3 | DIN/EN compositional name | European designation |
| AMS 5596 | Full SAE designation | For sheet, strip, foil, plate - solution annealed |
| AMS 5597 | Full SAE designation | For sheet, strip, foil, plate - precipitation hardened |
| AMS 5662 | Full SAE designation | For bar, forgings, rings - solution annealed |
| AMS 5663 | Full SAE designation | For bar, forgings, rings - precipitation hardened |
| AMS 5664 | Full SAE designation | For bar, forgings, rings - annealed |
| ASTM B670 | ASTM designation | Inconel 718 sheet, strip, and plate (non-aerospace) |
Why Source AMS 5596 from Fighter Jet Metals
Fighter Jet Metals supplies Inconel 718 sheet and plate to AMS 5596 with full mill certifications, heat-lot traceability, and AS9100D quality system compliance.
All material is supplied with certified mill test reports (CMTR) traceable to the origin heat and melt practice, signed certificate of conformance, and documentation suitable for aerospace first-article and production use.
VIM+VAR melt practice is confirmed on all certified mill test reports.
In-house processing available for AMS 5596 sheet and plate
Plate saw cutting (thickness and length/width cuts)
Shearing (sheet and thin plate)
Laser cutting
Custom blanks and near-net shapes
Certified Material for Critical Service
Materials supplied in 6Al-4V titanium must meet strict aerospace certification and traceability requirements. Fighter Jet Metals supports sourcing across a wide range of AMS, MIL, and OEM specifications, ensuring compliance with industry standards.
All material is supplied with full mill certifications, complete heat-lot traceability, and detailed documentation. This ensures reliability and suitability for safety-critical aerospace, defense, and high-performance engineering applications.